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Blades of the superalloy IN738 (CrMoTiAl LC) were tested on two cyclic stress levels, less and higher of the material fatigue limit. Fatigue cracking some blades took place on the second stage of the test at the blades airfoil base and in some distance from the base at the leading edge. Fractographic analyses have shown that in all sections crack origination was subsurface from inclusions because of sliding. This problem of the crack path has discussed and shown that the material state with high percent of inclusions caused earlier blades fatigue pre-cracking in very-high-cycle-fatigue regime during less level of cyclic loading. It has recommended and introduced new technology with less percent of inclusions for the superalloy that has increased its fatigue limit on 20% and fatigue cracking of blades have tested by the same program has seen on the second stage in the arifoil base section only.